Garmin G1000 Manual

							190-00709-04  Rev. AGarmin G1000 Pilot’s Guide for the Socata TBM 85087
FLIGHT INSTRUMENTS
UNUSUAL ATTITUDES
When the aircraft enters an unusual pitch attitude, red extreme pitch warning chevrons pointing toward the 
horizon	are	displayed	on	the	Attitude	Indicator,	starting	at	50˚	above	and	30˚	below	the	horizon	line.
Figure 2-52  Pitch Attitude Warnings
Nose High
Nose Low
If	
pitch	 exceeds	 +30˚/-20˚	 or	bank	 exceeds	 65˚,	some	 information	 displayed	on	the	 PFD	is removed.  The 
Altimeter	 and	Airspeed,	 Attitude,	Vertical	Speed,	and	Horizontal	 Situation	indicators	 remain	on	the	 display	
and	 the	Bearing	 Information,	 Alerts,	and	Annunciation	 windows	can	be	displayed	 during	such	situations.		 The	
following	information	 is	removed	 from	the	PFD	 (and	 corresponding	 softkeys	are	disabled)	 when	the	aircraft	
experiences unusual attitudes:
•	 Traffic  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev. A88
FLIGHT INSTRUMENTS
Blank Page  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 85089
ENGINE & AIRFRAME SYSTEMS
SECTION 3  ENGINE AND AIRFRAME SYSTEMS
 NOTE: Refer to the Pilot’s Operating Handbook (POH) for limitations.
The G1000 offers improved flight operations and reduces crew workload by automatically monitoring critical 
system parameters and providing system alerts during all phases of flight using the following:\
•	 The	Engine Indication System (EIS) displays electrical, fuel, engine, pressurization, and flight control 
information on the left side of the Multi Function Display (MFD).
•	Synoptics pages are provided for monitoring the status of the doors, de-icing systems, electri\
cal, and fuel.
•	 The	Crew Alerting System (CAS) displays advisories, cautions, and warnings to communicate conditions, 
statuses, and system failures.  CAS messages are grouped by level of importance and color-coded based on 
urgency and appear on the left side of the MFD.
In combination with these, aural alerts, additional avionics messages, a\
nd master indicators are used to inform 
the crew of aberrant flight conditions.  The system also provides an improved level of maintenance data for the 
ground crew.
Figure 3-1  Multi Function Display
EICAS Display  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A90
ENGINE & AIRFRAME SYSTEMS
In the event of a display failure, depending on the failed display(s), the functioning display(s) ma\
y be re-
configured to present Primary Flight Display (PFD) symbology together with engine and CAS informat\
ion 
(refer to the System Overview for more information about Reversionary Mode).  In Reversionary Mode, engine, 
pressurization, fuel, electrical, and trim data is presented in an abbreviated format on the left of the display.  
CAS messages appear in a window on the right of the display.  Synoptics are not available while in Reversionary 
Mode.
EIS
Display
CAS
Window
Figure 3-2  Reversionary Mode  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 85091
ENGINE & AIRFRAME SYSTEMS
3.1 ENGINE INDICATION SYSTEM (EIS)
Figure 3-4  EIS Display (Reversionary Mode)
17
1
5
6
4
3
2
9
8
12
13
15
16
1Torque
2Propeller Speed
3Generator Speed
4Interturbine Temperature
5Oil Pressure
6Oil Temperature
7CAS Display
8Cabin Pressure Altitude and Change Rate
9Differential Pressure
10Selected Cabin Altitude
11Oxygen Pressure
12Fuel Quantity
13Fuel Flow
14Fuel Pressure
15Battery and Generator Currents
16Battery and Essential Bus Voltages
17Elevator, Aileron, and Rudder Trim and Flap 
Position
Figure 3-3  EIS Display (Normal Mode)
4
3
2
1
8
9
10
6
5
7
11
12
13
14
15
16
17  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A92
ENGINE & AIRFRAME SYSTEMS
EIS information is presented using gauges, horizontal and vertical bar indicators, slide bars\
, and digital readouts.  
Green ranges on the instrument scales indicate normal ranges of operation;\
 yellow and red bands indicate caution 
and warning, respectively.  During normal operating conditions, an instrument’s pointer appears in white and the 
readout text is green.  When data is out of the range of the indicator or gauge, the point\
er moves to the end of the 
scale; digital readouts display as “---” (dashes).
When an unsafe operating condition occurs, the pointer and readout color change to yellow or flash red, 
indicating a caution or warning.  If a cautionary time limit is exceeded, the sliders, pointers, and digits may flash \
red, even if the parameter is still within in the cautionary range (refer to each display description for details).  If 
the sensor data for a parameter becomes invalid or unavailable, a red “X” is displayed across the indicator and/or 
readout.
ENGINE PARAMETERS
The TBM 850’s EIS displays torque, propeller speed, generator speed, and interturbine temperature using arc 
gauges.
TORQUE GAUGE
The Torque Gauge displays values from 0 to 130% of maximum safe torque.  If the torque remains above 
121.4% for more than 5 seconds or exceeds the value indicated by the red tick mark, a warning condition 
occurs.  The maximum climb torque is displayed as a white triangle (bug) while the optimum cruise ra\
nge is 
displayed as a white band on the Torque Gauge.  When bleed pressure reaches its upper limit, ‘BLEED HI’ is  
annunciated above the Torque Gauge.
Figure 3-5  Torque Gauge
Maximum Climb TorqueOptimum Cruise Range
PROPELLER RPM GAUGE
Propeller speed is shown in revolutions per minute (rpm) from zero to 2200.  If propeller speed slows 
to where the gauge pointer enters the yellow range, a caution is issued.  A propeller overspeed warning is 
indicated if propeller speed exceeds the maximum safe operating speed.
Figure 3-6  Propeller RPM Gauge  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 85093
ENGINE & AIRFRAME SYSTEMS
GENERATOR SPEED GAUGE
Generator speed is indicated as a percentage of maximum safe operating speed (rpm), from 0 to 120%.  If 
generator speed exceeds 104% a warning condition occurs.
Figure 3-7  Generator Speed Gauge
ITT GAUGE
The Interturbine Temperature (ITT) Gauge ranges differ for engine off/start and running conditions.  Values 
between 200 and 1200 degrees Celsius (°C) are shown at engine start; values change to 200 to 900°C when 
the engine starts running.  When the engine is not running, ‘OFF’ \
is annunciated above the ITT readout; this 
changes to ‘STRT’ upon engine start.  No annunciation is shown when the engine is ru\
nning normally.
Figure 3-8  Interturbine Temperature Gauge Status Annunciations
Engine StartNormalEngine Off
Temperatures above which warnings occur are indicated by red tick marks along the ITT Gauge.  Refer to 
comments for the ‘ITT’ CAS message in Table 3-5 for warning issuance criteria.
OIL  PRESSURE AND TEMPERATURE  GAUGES
Engine oil pressure and temperature are shown along horizontal bar indicators below the engine gauges.  
Oil pressure is shown in pounds per square inch (psi) and temperature in degrees Celsius (°C).
Figure 3-9  Oil Pressure and Temperature Gauges  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A94
ENGINE & AIRFRAME SYSTEMS
CABIN PRESSURIZATION
Cabin pressurization information (cabin altitude, rate of change, and differential cabin pressure) is shown at 
the top of the right EICAS column.  Only readouts for cabin altitude and pressure differential are displayed in 
Reversionary Mode.
Cabin altitude (ALT FT) is shown on a color-coded scale labeled in 5,000-ft increments with a readout (in 
feet) below.  Cabin altitude change rate (RATE FPM) is displayed on a scale in terms of 2,000 fpm increments 
with a readout (in fpm) below.  Cabin pressure differential (DIFF PSI), in pounds per square inch (psi), is 
indicated on a color-coded scale with a readout.  Selected Cabin Altitude is displayed as a digital readout (in 
100 ft increments) with a range from -1,000 to 11,000 feet.
Figure 3-10  Cabin Pressure Display
Pressure 
Altitude Pressure 
Change  Rate
Pressure 
Differential
Oxygen 
Pressure
Selected
Cabin
Altitude
The pressure (in psi) for the oxygen system is given as a readout below the cabin pressurization display under 
normal display conditions.
FUEL INFORMATION
The fuel display is located beneath the oxygen pressure readout and shows the fuel quantity in each tank (in 
United States gallons, USG), fuel flow (gallons per hour, gph), and fuel pressure (psi).  Fuel quantity for each 
tank is normally shown along a slider scale.  Readouts for fuel quantity\
 and fuel flow are shown in Reversionary 
Mode.
Fuel
Flow Fuel
Pressure
Figure 3-11  Fuel Display
Tank Fuel 
Quantities  
						

							190-00709-04  Rev.  AGarmin G1000 Pilot’s Guide for the Socata TBM 85095
ENGINE & AIRFRAME SYSTEMS
ELECTRICAL INFORMATION
Currents for the battery (pointers labeled “B”) and generator (pointer labeled “G” for primary generator and 
“S” for standby generator) and voltages for the battery and essential bus (pointer labeled “E”) are shown along 
color-coded scales, with readouts to the right.
GeneratorCurrent
Essential
Bus Voltage Battery
Voltage Battery
Current
Figure 3-12  Electrical Display
TRIM AND FLAP INDICATORS
Elevator, rudder, and aileron trim indications are shown along slide bar scales next to the CAS messages 
in normal display mode.  Flap deflection is normally displayed beneath\
 the trim indications using a rotating 
pointer.  Flap positions for takeoff, landing, and up positions are labeled.  In Reversionary Mode, only elevator 
trim is indicated and flap position (UP, T/O, LDG) is provided as a digital readout.
Figure 3-13  Trim and Flap Indications  
						

							Garmin G1000 Pilot’s Guide for the Socata TBM 850190-00709-04  Rev.  A96
ENGINE & AIRFRAME SYSTEMS
3.2 SYNOPTICS
The Synoptics pages show current conditions of certain aircraft functionality on aviation system diagrams,  
reducing workload by allowing the flight crew to rapidly analyze the situation.  Aircraft systems graphically 
depicted in the synoptic diagrams include:
•	 Electrical
Once the SYSTEM Softkey is selected, the Synoptics pages can be accessed using softkeys\
 or the small FMS 
Knob.  To return to the previously displayed page when a Synoptics Page has been displayed, select\
 the SYSTEM 
Softkey or CLR Key, or turn the large FMS Knob.
SYSTEM 
SYSTEM CAS MAP ELEC CHKLIST  FUEL GEN 
Figure 3-14  Synoptic Pages Softkeys
• SYSTEMAccesses the Synoptics page softkeys
• ELECDisplays the Electrical Synoptics Page
• FUELDisplays the Fuel Synoptics Page
• GENDisplays the General Synoptics Page for the de-ice system and doors
Map
Synoptic Page
Figure 3-15  MFD LayoutEICAS